EP2362072A2 - Schmiermittelkühlung für Turbinenstarter - Google Patents

Schmiermittelkühlung für Turbinenstarter Download PDF

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Publication number
EP2362072A2
EP2362072A2 EP11155261A EP11155261A EP2362072A2 EP 2362072 A2 EP2362072 A2 EP 2362072A2 EP 11155261 A EP11155261 A EP 11155261A EP 11155261 A EP11155261 A EP 11155261A EP 2362072 A2 EP2362072 A2 EP 2362072A2
Authority
EP
European Patent Office
Prior art keywords
starter
lubricant
volume
turbine
transfer passages
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11155261A
Other languages
English (en)
French (fr)
Inventor
Robert Telakowski
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of EP2362072A2 publication Critical patent/EP2362072A2/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the subject matter disclosed herein generally relates to pneumatic turbine starters. More specifically, the subject disclosure relates to cooling of pneumatic turbine starter lubricant.
  • Aircraft engines for example, gas turbines, are typically equipped with an air-driven or gas driven turbine starter mounted on the engine accessory gearbox.
  • the functional purpose is to accelerate the engine up to a desired speed prior to ignition of the engine combustor.
  • the turbine starter is typically driven by pressurized air provided by an air source such as an auxiliary power unit, another operating engine, or an external air cart connected to the turbine starter. Pressurized air or gas fed into the turbine starter drives rotation of starter turbine blades causing rotation of a starter shaft.
  • the starter shaft transmits this rotation to the drive shaft of the accessory gearbox.
  • Rotation of the gearbox shaft drives rotation of a high pressure rotor of the engine which induces airflow into the engine and causes rotation of the engine low pressure rotor assembly. When the engine rotation reaches a desired speed, combustion is initiated.
  • Typical turbine starters include a lubrication system which delivers lubricant such as oil to the rotating elements of the turbine starter via, for example, a splash system or an oil pump internal to the turbine starter.
  • lubricant such as oil
  • the service life of the lubricant, and the starter itself, is often limited by the hot/hostile environment of the installation and such installation does not provide cooling of the lubricant that would extend its life, and consequently the life of the starter.
  • Active cooling systems including oil coolers, pumps, filters, etc. are disadvantageous due to weight, packaging size, cost and reliability problems associated with such systems.
  • Other lubrication systems occasionally used in starters mingle lubricant of the engine gearbox with that of the starter to cool the starter lubricant. This approach has disadvantages, however, in that it exposes the gearbox and engine cooling systems to contamination from the starter in the event of starter damage and/or failure.
  • the art would well receive an alternative cooling system for turbine starter lubricant
  • a cooling system for turbine starter lubricant includes one or more outflow transfer passages extending from the turbine starter to a secondary component. At least one heat exchange passage is located in the secondary component affixed at a first end to an end of an outflow transfer passage of the one or more outflow transfer passages, the secondary component having a lower interior temperature than the turbine starter.
  • One or more return transfer passages are affixed to a second end of the at least one heat exchange passage and extend from the secondary component to the turbine starter.
  • Flowing a volume of starter lubricant through the one or more outflow transfer passages, the at least one heat exchange passage, and the one or more return transfer passages removes thermal energy from the volume of starter lubricant and returns the volume of starter lubricant to the turbine starter.
  • a method of cooling lubricant of a turbine starter includes flowing a volume of starter lubricant from the turbine starter to a secondary component via one or more outlet transfer passages.
  • the starter lubricant is flowed through at least one heat exchange passage disposed in the secondary component which has a lower interior temperature than the turbine starter, thereby removing thermal energy from the starter lubricant.
  • the volume of starter lubricant is returned to the turbine starter via one or more return transfer passages.
  • the turbine starter 10 includes a turbine wheel 12 that is driven by a compressed gas, from a source such as an auxiliary power unit (APU), another operating engine, or an external air cart.
  • the turbine starter 10 has a gear housing 14 disposed between and mounted to an inlet housing 16 and a transmission housing 18.
  • the inlet housing 16 defines a flow chamber 20 having a flow inlet 22, through which the compressed gas enters the turbine starter 10, and a flow outlet 24.
  • the turbine wheel 12 is disposed in the flow chamber 20 between the flow inlet 22 and the flow outlet 24 and includes a plurality of blades 26 disposed circumferentially around the turbine wheel 12.
  • the turbine wheel 12 further includes a central axially-extending starter shaft 28.
  • the turbine wheel 12 is mounted to the starter shaft 28 such that the starter shaft 28 is driven in rotation about its axis as the turbine wheel 12 is driven to rotate about its axis by the compressed gas passing through the plurality of blades 26 to the flow outlet 24.
  • a flow deflector 34 may be disposed in the flow chamber 20 downstream of the turbine wheel 12 to direct the compressed gas toward the flow outlet 24.
  • the energy extracted from the compressed gas via the turbine wheel 12 is transmitted via the starter shaft 28 into an output shaft 36 operably connected to an engine gearbox shaft 38 of an engine gearbox assembly 40.
  • the engine gearbox assembly 40 is also referred to herein as a secondary component 40 with respect to the turbine starter 10.
  • a starter lubricant 42 for example, oil
  • the turbine starter 10 generates a substantial amount of heat in its operation, much of this heat is transferred to the starter lubricant 42 as it is flowed throughout the turbine starter 10. To extend its useful life, it is desired to periodically cool the starter lubricant 42. Because the environment of the engine gearbox assembly 40 is at a lower temperature than that of the turbine starter 10, the engine gearbox assembly 40, specifically engine gearbox coolant 44, is utilized as a heat sink to cool the starter lubricant 42.
  • Starter lubricant 42 pools in a lubricant sump 46 inside of the turbine starter 10 where the rotating elements, for example, a gear assembly 48, pick up an amount of starter lubricant 42 while passing through the lubricant sump 46.
  • a clutch 66 decouples the turbine starter 10 from the engine gearbox assembly 40, so the gear assembly 48 does not continue to rotate.
  • a splash guard 68 continues to rotate with the engine gearbox shaft 38 to distribute starter lubricant 42.
  • One or more lubricant troughs 50 are disposed in the turbine starter 10, in some embodiments, near a top 52 of the turbine starter 10.
  • At least one heat exchange pipe 56 is connected to an engine gearbox end 58 of each transfer passage and passes through the engine gearbox assembly 40 and is connected to one or more return transfer passages 60 that extend from the engine gearbox assembly 40 back into the turbine starter 10.
  • the at least one heat exchange pipe 56 includes a plurality of fins 62 extending outwardly therefrom to promote heat transfer.
  • Starter lubricant 42 flows, in some embodiments, naturally via gravity, from the lubricant troughs 50 through the one or more outflow transfer passages 54 and into the at least one heat exchange pipe 56.
  • heat from the starter lubricant 42 is transferred to the heat exchange pipe 56 and dissipated into the engine gearbox coolant 44 flowing around an exterior of the heat exchange pipe 56. Its temperature lowered via this heat exchange, the starter lubricant 42 flows through the one or more return transfer passages 60 into the turbine starter 10 and the lubricant sump 46.
  • some embodiments or turbine starters 10 utilize an internal pump 64 to circulate the starter lubricant 42 throughout the turbine starter 10, rather than a splash system as shown in FIG. 1 .
  • the internal pump 64 is utilized, for example, in turbine starters 10 where there is a desire to direct starter lubricant 42 to key elements, for example, bearings, gear assembly 48, and/or clutch 66.
  • heated starter lubricant 42 is pumped, via the internal pump 64, through the one or more outflow transfer passages 54 and into the at least one heat exchange pipe 56.
  • the starter lubricant 42 flows through the heat exchange pipe 56, heat from the starter lubricant 42 is transferred to the heat exchange pipe 56 and dissipated into the engine gearbox coolant 44 flowing around an exterior of the heat exchange pipe 56. Its temperature lowered via this heat exchange, the starter lubricant 42 flows through the one or more return transfer passages 60 into the turbine starter 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)
  • Gear Transmission (AREA)
EP11155261A 2010-02-22 2011-02-21 Schmiermittelkühlung für Turbinenstarter Withdrawn EP2362072A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/709,961 US8910463B2 (en) 2010-02-22 2010-02-22 Turbine starter lubricant cooling

Publications (1)

Publication Number Publication Date
EP2362072A2 true EP2362072A2 (de) 2011-08-31

Family

ID=44147639

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11155261A Withdrawn EP2362072A2 (de) 2010-02-22 2011-02-21 Schmiermittelkühlung für Turbinenstarter

Country Status (3)

Country Link
US (1) US8910463B2 (de)
EP (1) EP2362072A2 (de)
CA (1) CA2732330A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3015572A1 (fr) * 2013-12-23 2015-06-26 Microturbo Demarreur a air de turbomachine comportant des premier et deuxieme compartiments de lubrification
EP3495630A1 (de) * 2017-10-26 2019-06-12 Hamilton Sundstrand Corporation Zusatzschmiersystem für pneumatische starter

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8910463B2 (en) * 2010-02-22 2014-12-16 Hamilton Sundstrand Corporation Turbine starter lubricant cooling
US9140194B2 (en) * 2012-01-11 2015-09-22 Honeywell International Inc. Gas turbine engine starter-generator with integrated lube oil scavenge functionality
FR3011277B1 (fr) * 2013-09-30 2018-04-06 Turbomeca Turbomachine adaptee a fonctionner en mode vireur
EP3094845B1 (de) * 2014-01-15 2020-04-29 United Technologies Corporation Kühlsysteme für gasturbinenmotoren
US9917490B2 (en) * 2014-11-21 2018-03-13 Hamilton Sundstrand Corporation Tail cone generator with integral speed increasing gearbox
US10247105B2 (en) 2016-01-08 2019-04-02 Hamilton Sundstand Corporation Air turbine starter with lubrication valve
EP3885537A1 (de) * 2020-03-26 2021-09-29 Unison Industries LLC Haltesystem für luftturbinenstarter und verfahren zur herstellung solches systems
PL433601A1 (pl) * 2020-04-20 2021-10-25 Unison Industries, Llc Układ smarowania komponentów w rozruszniku silnika
PL434997A1 (pl) * 2020-08-18 2022-02-21 Unison Industries, Llc Rozrusznik turbiny powietrznej
US12000342B2 (en) 2022-07-12 2024-06-04 General Electric Company Air turbine starter with lubrication recirculation circuit

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3015572A1 (fr) * 2013-12-23 2015-06-26 Microturbo Demarreur a air de turbomachine comportant des premier et deuxieme compartiments de lubrification
WO2015097380A1 (fr) * 2013-12-23 2015-07-02 Microturbo Démarreur à air de turbomachine comportant des premier et deuxième compartiments de lubrification
EP3495630A1 (de) * 2017-10-26 2019-06-12 Hamilton Sundstrand Corporation Zusatzschmiersystem für pneumatische starter

Also Published As

Publication number Publication date
US8910463B2 (en) 2014-12-16
US20110203249A1 (en) 2011-08-25
CA2732330A1 (en) 2011-08-22

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